33results about How to "Strong engineering realization" patented technology

The invention relates to an integrated correcting system and correcting method applied to different active array antennas. The integrated correcting system includes an active array antenna, a high-precision measurement real-time compensation unit, a testing probe, an industrial personal computer, a vector network analysis meter, a RF cable, and a low frequency cable. According to the invention, the integrated correcting system is advantaged by high correcting precision, short correcting time, simplicity and easiness of implementation, strong universality and excellent industrial reliability.

A mixed switching structure suitable for a satellite-borne processing transponder comprises entry port processing units, a sharing buffer, a space division switching unit, a switching control unit and frame shapers. Then entry port processing units perform adaptation and sorting processing on time slot frames, and output two paths after processing, a path of continuous time slot frames are sent to the space division switching unit, and a path of packet data stream is sent to the sharing buffer; the sharing buffer is used for distribution and mapping management of buffer memory space, and outputs corresponding packets to the frame shaper of a specified port according to a dispatching instruction; the space division unit sends time slots of the entry port to the frame shaper according to control information; the frame shaper puts the time slots in a specified time slot cache region, the packets output by the sharing buffer are packaged to unoccupied business time slots according to priority, and data serial output of the specified time slot cache region is read according to a frame start sending instruction. The mixed switching structure suitable for the satellite-borne processing transponder can support a circuit switching service and a packet switching service of various speeds, and can support any ratio of the two services.

The invention provides a step-by-step adjustable air inlet duct by means of moving a sliding block to adapt to a working mach number state and an air inlet duct adjusting method. The step-by-step adjustable air inlet duct comprises an air inlet duct main body, a sliding block, a sliding device, a driving mechanism and a locking mechanism, wherein the air inlet main body consists of a part of an outer surface of an elastic body and an air inlet duct outer cover, the inner surface of the air inlet duct is provided with the sliding device, the sliding block is connected with the sliding device and slides along the sliding device by power provided by the driving mechanism, and when the sliding block slides to a proper position, the locking mechanism locks the sliding block, so that the technical problem that an air inlet duct in a complex profile structure cannot be adjusted in the prior art is solved.

The invention discloses a space debris tethered dragging deorbiting target attitude nutation suppression control method and system, and belongs to the field of spacecraft attitude dynamics and control. The implementation method comprises the following steps: after assuming that a fragment target and a rope net assembly adopt a rigid body, establishing a kinetic model of a tethered dragging systemby adopting an Euler equation of rigid body rotation motion; analyzing and designing a constant tension switching control method based on dissipation of mechanical energy; indirectly reflecting the motion of the rope node by measuring the distance between the rope node and the connecting line of the two satellites or observing the included angle between the tether direction and the connecting lineof the two satellites, and providing a basis for selection of switching conditions of a switching tension control method. The method is used for quickly and effectively inhibiting the posture nutation of the debris target in the dragging deorbiting process after the space debris is subjected to flying net capture, it is guaranteed that the risks of tether winding and the like do not occur in thedragging process, and a technical support is provided for safely and efficiently completing the space debris active clearing task.

The invention relates to the technical field of air vehicles and in particular relates to an air vehicle airfoil folding mechanism. The air vehicle airfoil folding mechanism comprises a transformationsystem, wherein the transformation system is arranged between a fuselage and a wing of the air vehicle; the transformation system comprises a plurality of groups of folding hinges and a plurality offolding planes; the transformation system is movably connected with the fuselage and the wing of the air vehicle respectively through the folding hinges; in a transformation process of the transformation system, a front edge of the wing can keep moving along a tail edge of the transformation system all the time; advanced aerodynamic properties of a forward-swept wing and a folding wing are integrated to realize a novel forward-swept wing and folding wing combinatory transformation manner; the flight stability and the wide-speed-region flight performance are improved.

The invention discloses an adjustable throttling device for simulating a spraying pipe of an aero-engine. The adjustable throttling device comprises a spraying pipe body, an axial normal-open throughhole, a lateral adjustable through hole, an adjusting assembly and a fixing assembly, wherein the spraying pipe body comprises an axial inlet end and an axial outlet end, the axial normal-open throughhole is located at the axial outlet end of the spraying pipe body, the lateral adjustable through hole is formed in the spraying pipe body in the peripheral direction, the lateral adjustable throughhole is closer to the axial inlet end of the spraying pipe body compared with the normal-open through hole, the adjusting assembly is used for adjusting the hole size of the lateral adjustable throughhole, therefore the throttling working condition of the spraying pipe of the aero-engine is simulated, and the fixing assembly fixes the adjusting assembly to the spraying pipe body.

The invention belongs to the field of aero-engine tests, and relates to a tail nozzle temperature field visualization device based on binocular vision and an identification method thereof. The tail nozzle temperature field visualization device comprises a cooling probe, a top black background plate, and a processor storing temperature field measurement and tail nozzle recognition post-processing programs, wherein the cooling probe is located at the lower position of the central axis of the engine tail nozzle; a binocular camera is arranged in the cooling probe; the binocular camera has a top view angle along the axial direction of the cooling probe and a side view angle along the radial direction of the cooling probe; the top black background plate is located within the top view angle; theengine tail nozzle is positioned within the side view angle; and the binocular camera of the cooling probe sends a shot image to the processor, so that the image is processed according to a processing program stored in the binocular camera, and a temperature field of the combustion chamber is obtained.

The invention relates to the field of aircraft ground simulation, and provides a space non-cooperative target capture and control and assembly control test device and method, and the device comprises a simulation upper computer, a visual positioning system, a tracking star simulation system, and a target star simulation system. Wherein the simulation upper computer is used for sending a control instruction to the tracking star simulation system and/or the target star simulation system; the visual positioning system is used for acquiring pose information of the tracking star simulation system and/or the target star simulation system and feeding back the information to the tracking star simulation system and/or the target star simulation system; the tracking star simulation system is used for receiving a control instruction of the simulation upper computer, capturing the target star simulation system and measuring and calculating disturbance characteristics in the capturing process. The spatial non-cooperative target capture, control and assembly control test device is established, disturbance characteristics in the capture process can be calculated, assembly control can be achieved, problems in scheme design can be found, and algorithm performance can be analyzed and verified.

The invention discloses an ultraviolet continuous zoom telescopic optical system which comprises a front fixed lens group, a zoom lens group, a compensation lens group and a rear fixed lens group which are sequentially arranged from an object space to an image space, and an aperture diaphragm is arranged between the compensation lens group and the rear fixed lens group and is close to the rear fixed lens group. According to the invention, continuous zooming can be realized, the focal length variation range is 120-480 mm, the zooming range is large, and the consistency of system resolution and the stability of imaging performance are realized under different focal lengths; the invention provides an ultraviolet telescopic optical system with a fixed F number and a large zoom ratio, the F number of the system is 4.5, and the zoom ratio is 4. All the lenses are spherical lenses.